JP6131711B2 - Projectile - Google Patents

Description

  The present invention relates to a projectile charge in which a triple base propellant is accommodated in a burnout container, which is used for an ammunition for a gun such as an a howl cannon.

  In general, in an ammunition for artillery such as an a howl cannon, a bullet (a flying object) is caused to fly by a combustion gas pressure obtained by burning a propellant. Such bullets include fixed bullets that are fixed to shells filled with propellants inside, and separate-loading bullets that use a projectile charge containing propellants inside as a separate body from the bullets. Divided. The propellant is composed of a burnout container that is burned off by combustion, a propellant that generates combustion gas, an ignition agent for igniting the propellant, and the like. In the case of separate-loading bullets, a plurality of projectiles are arranged according to the desired range of the projectile, and each projectile is arranged on a central axis of a cannon, such as a firing tube. It is ignited by an igniter. Therefore, in order to smoothly propagate the flame generated from the igniter to the igniting agents of all the connected propellants, the radial central portion of the propellant has an axial through hole, An ignition powder is disposed on the inner peripheral surface of the hole. In addition, each projectile charge is generally a module type so that it can be connected to each other in the axial direction.

  By the way, the triple base propellant is often used for the propellant contained in the above-mentioned projectile. The triple base propellant was developed for the purpose of reducing the erosion (burning) of the barrel by reducing the combustion temperature and reducing the muzzle flame while increasing the explosive power. The triple base propellant is mainly composed of nitrocellulose, nitro plasticizer, and nitroguanidine, and may contain additives such as stabilizers, flame retardants, and brighteners as necessary.

  Further, as the nitro plasticizer, nitroglycerin having high explosive properties is generally used. For example, Patent Document 1 also uses, as a main propellant, a triple base propellant containing nitroglycerin as a nitro plasticizer as a propellant for a propellant. In addition, in Patent Document 1, an initial velocity stabilizing propellant having a gas generation rate faster than that of the main propellant is contained in the burnout container together with the main propellant. Thereby, it is supposed that the initial velocity at the time of bullet shooting is stabilized and abnormal pressure such as a negative pressure difference in the barrel can be suppressed.

  On the other hand, Non-Patent Document 1 describes that diethylene glycol dinitrate can also be used as a nitro plasticizer of a triple base propellant.

Japanese Patent Application Laid-Open No. 2012-21685

Edited by the Institute of Ballistic Science, “Firearm Ammunition Technology Handbook (Revised)”, published by the Defense Technology Association, February 2, 2005, P351-352

  The propellant of Patent Document 1 is intended to prevent the stopping of the bullet and stabilize the initial velocity of the bullet by accommodating the propellant for stabilizing the initial velocity, which has a higher gas generation rate than the main propellant, in the burnout container. However, since nitroglycerin with high explosive properties is used as a nitro plasticizer, there is a problem in safety during handling and storage.

  On the other hand, if it is a triple base propellant using diethylene glycol dinitrate as a nitro plasticizer as described in Non-Patent Document 1, the safety during handling and storage is high. However, diethylene glycol dinitrate has a tendency to lower the ignition ability as the temperature becomes lower. Therefore, when a triple base propellant containing diethylene glycol dinitrate is used, there are problems that the ignitability of the entire propellant is poor during low-temperature shooting and that the ignition delay time is also long.

  Therefore, the present inventors, as a result of earnestly examining whether to improve the ignitability during low-temperature shooting even when using a triple base propellant using highly safe diethylene glycol dinitrate, as a result of the main propellant than In addition, the inventors have found that the above problem can be solved by using an ignition auxiliary propellant having a short ignition delay time and a gas generation rate slower than that of the main propellant, and have completed the present invention.

  That is, an object of the present invention is to provide a projectile charge that has high safety during handling and storage and is also excellent in ignitability during low-temperature shooting.

  As a means for this, the present invention is a propellant in which a main propellant composed of a triple base propellant containing diethylene glycol dinitrate as a nitro plasticizer is contained in a burnout container, Contains an ignition aid propellant containing nitrocellulose together with the main propellant. In addition, the ignition auxiliary propellant is characterized in that the ignition delay time is shorter than that of the main propellant and the gas generation rate is slower than that of the main propellant. The “ignition delay time” and “gas generation rate” are determined when the main propellant and the auxiliary ignition propellant are loaded in a sealed bomb test apparatus having a constant combustion volume so that the specific gravity is 0.1 g / cc. The ignition delay time and the gas generation rate in the combustion test are meant. (Details of the sealed bomb test apparatus and test method will be described later.)

  In this way, by using triple base propellant as the main propellant, it is possible to radically reduce the erosion of the gun barrel by suppressing the combustion temperature than when using other explosives . It is also possible to increase gunpowder power and muzzle flame. In addition, since the main propellant uses diethylene glycol dinitrate as a nitro plasticizer, misexplosion during handling and storage can be avoided and safety is also high. However, diethylene glycol dinitrate has lower ignition ability at low temperatures than nitroglycerin. Therefore, the ignition delay time is shorter than the main propellant, that is, the flame propagation speed is faster than the main propellant, and the gas generation rate is slower than the main propellant, that is, the amount of combustion gas generated per unit time is the main firing. By using a smaller number of auxiliary ignition propellants than the main propellant in combination with the main propellant, good ignitability can be ensured even during low-temperature shooting such as below freezing.

  In order to make the ignition delay time of the ignition auxiliary propellant shorter than that of the main propellant, the relative ratio of nitrocellulose in the ignition auxiliary propellant may be made higher than that of the main propellant. If the relative proportion of nitrocellulose is higher than the main propellant, a triple-base or multi-base propellant can be used as an ignition aid propellant. Alternatively, single-base or double-base propellants can be used as ignition assisting propellants. Single-base and double-base propellants inherently have a higher relative proportion of nitrocellulose than triple-base propellants.

  On the other hand, in order to make the gas generation rate of the ignition auxiliary propellant slower than that of the main propellant, the web size of the ignition auxiliary propellant may be made larger than that of the main propellant. The web size is the distance between adjacent holes and the distance from the hole to the outer peripheral surface of each propellant particle (Ministry of Defense standard ammunition term NDSY 0001D), and the distance between the opposing surfaces that the flame contacts. (See FIG. 4).

  In addition, it is preferable that the usage-amount (accommodation amount) of the said ignition auxiliary propellant shall be 5-25 mass% with respect to 100 mass% of mass sum total of the said main propellant and the said ignition auxiliary propellant. If the amount of ignition auxiliary propellant used is too small, the ignitability during low-temperature shooting cannot be improved effectively. Conversely, if the amount of ignition auxiliary propellant used is too large, erosion of the gun barrel tends to occur. Because.

  The burnout container has an axial through hole in the radial center, and an ignition powder is disposed on the inner peripheral surface of the burnout container. Therefore, it is preferable to arrange the ignition auxiliary propellant at least on the innermost peripheral edge in the burnout container. Since the ignition auxiliary propellant supplements the ignitability of the main propellant, if the ignition auxiliary propellant is arranged at a site away from the ignition agent, the effect of this cannot be fully utilized.

  According to the launching charge of the present invention, the safety during handling and storage is high, and the ignitability during low-temperature shooting is also excellent.

1 is a cross-sectional view of Embodiment 1. FIG. 6 is a cross-sectional view of a second embodiment. FIG. It is sectional drawing of the sealing bomb test apparatus used in a combustion measurement test. It is a top view of the propellant grain explaining web size.

  Hereinafter, typical embodiments of the present invention will be described. As shown in FIGS. 1 and 2, the propellant 10 of the present invention contains a main propellant 12 and an ignition auxiliary propellant 13 in a burn-out container 11, and a dot is placed in a through hole 14 in the center in the radial direction. Gunpowder 15 is arranged.

  The burnout container 11 is burned down by combustion, and is a thick cylindrical container (having a large internal space width) having an axial through hole 14 at the radial center. The burnout container 11 holds a bottomed cylindrical storage case 11a for storing the main propellant 12 and the ignition auxiliary propellant 13, a lid 11b for closing the opening of the storage case 11a, and the ignition charge 15. It consists of a gunpowder cylinder 11c. The distal end portion 11d of the burnout container 11 (accommodating case 11a) is slightly reduced in diameter as compared with other portions, and the reduced diameter portion 11d is the proximal end portion (lid 11b) of the other propellant 10. ) Is a module type that can connect a plurality of propellants 10 in the axial direction.

  The ignition cartridge 11c is a cylindrical member, and is disposed in the axial direction to the radial center of the housing case 11a, thereby defining a part of the inner peripheral wall of the through hole 14. In addition, an ignition powder 15 ignited by an ignition device (not shown) is fixed to the inner peripheral surface of the ignition cylinder 11c in a state of being packed in a medicine bag.

  The burnout container 11 (the storage case 11a, the lid 11b, and the ignition cartridge 11c) is mainly composed of nitrocellulose or kraft pulp, and these are formed into a container shape with a binder resin. As the binder resin, styrene butadiene latex, acrylic resin, polyethylene, polystyrene, polyamide, polybutadiene, polyurethane and the like can be used. Moreover, it is also preferable to add a stabilizer for suppressing the spontaneous decomposition of nitrocellulose to the burnout container 11. Examples of the stabilizer include ethyl central, diphenylamine, and methyldiphenylurea.

  The main propellant 12 is a triple base propellant mainly composed of nitrocellulose (NC), nitro plasticizer, and nitroguanidine (NQ). In the present invention, diethylene glycol dinitrate (DEGN) is used as the nitro plasticizer. Has been. Moreover, additives, such as a stabilizer, a flame retardant, and a brightener, can also be added as needed. Examples of the stabilizer include ethyl central, examples of the flame retardant include potassium sulfate and cryolite, and examples of the brightener include graphite.

  The main propellant 12 is for injecting bullets (flying bodies) (not shown) with combustion gas generated upon combustion, and is contained in a large amount in the projectile charge 10. For this reason, if the combustion temperature is high, the erosion of the gun barrel becomes intense and the number of gun barrels is shortened. Therefore, the composition ratio must be such that the combustion temperature does not increase. Therefore, by using the main propellant 12 consisting of triple base propellant, while increasing the explosive power, the combustion temperature is suppressed and the erosion (burning) of the barrel is reduced, and the muzzle flame is reduced. Can be planned. In addition, the use of DEGN as a nitro plasticizer also increases the safety during handling and storage. However, when DEGN is used, the lower the temperature, the lower the ignitability during shooting. In addition, if it is a very small amount, it is not denied that nitroglycerin (NG) is also used as a nitro plasticizer, but it is preferable not to contain NG.

  The main propellant 12 is formed in a granular shape of a predetermined shape, and a large number of the granular main propellant 12 is accommodated in the burnout container 11. The shape of the main propellant 12 is not particularly limited as long as it is a shape conventionally used in this type of propellant, for example, spherical, cylindrical non-porous, cylindrical single hole, cylindrical 7 hole, cylindrical 19 hole, hexagonal 19 holes can be used. In order to generate a large amount of combustion gas quickly, a perforated shape such as a cylindrical single hole, a circular cylinder 7 hole, a circular cylinder 19 hole, or a hexagonal 19 hole is preferable, and among them, a cylindrical 19 hole or a hexagonal 19 hole is particularly preferable.

  The ignition auxiliary propellant 13 is used in combination to supplement the low temperature ignitability of the main propellant 12. Therefore, the auxiliary ignition propellant 13 uses an ignition delay time shorter than at least the main propellant 12. Preferably, about 5 to 60% of the ignition delay time of the main propellant 12 is used. This is because if the ignition delay time is longer than the main propellant 12, there is no effect of improving the ignitability of the main propellant 12, and the ignition delay time cannot be improved.

  As such an ignition auxiliary propellant 13, any composition having a higher relative proportion of nitrocellulose (NC) than the main propellant 12 may be used. This is because the ignition delay time of NC is faster than that of other explosive components, and the influence on the ignition auxiliary propellant 13 as a whole is great. As long as the composition has a higher relative proportion of nitrocellulose than the main propellant 12, a known multi-base launch containing a triple-base propellant similar to the main propellant 12, explosive components such as RDX, and high-energy substances Drugs can also be used. Moreover, a single base propellant and a double base propellant can also be used suitably. In general, single-base propellants are mainly composed of nitrocellulose, and double-base propellants are mainly composed of nitrocellulose and nitroglycerin, which is inherently higher in relative proportion of NC than triple-base propellants. . In addition, since the ignition auxiliary propellant 13 is used in a small amount as an auxiliary agent for the main propellant 12, it is not necessary to consider much the restriction on the combustion temperature.

  Further, the gas generation speed of the ignition auxiliary propellant 13 needs to be slower than that of the main propellant 12. When the gas generation speed of the ignition auxiliary propellant 13 is faster than that of the main propellant 12, the ignition auxiliary propellant 13 burns out before the main propellant 12 is reliably ignited, and the ignitability of the main propellant 12 is improved. It becomes difficult to make it. However, on the other hand, if the gas generation rate of the ignition auxiliary propellant 13 is too slow than the main propellant 12, the ignition auxiliary propellant 13 may not burn out until a bullet is ejected from the muzzle, and a combustion residue may be generated. There is. Therefore, black powder cannot be used as the ignition auxiliary propellant 13 because the gas generation speed is extremely slow. With the ignition auxiliary propellant 13 containing nitrocellulose, an appropriate gas generation rate can be secured. In view of the above tendency, the gas generation rate of the ignition auxiliary propellant 13 is specifically preferably 30 to 99%, more preferably 50 to 90% with respect to the gas generation rate of the main propellant 12.

  The gas generation speed can be adjusted by the shape of the ignition auxiliary propellant 13 (more precisely, the web size W). That is, the ignition auxiliary propellant 13 is also formed into a granular shape like the main propellant 12, and a large number of the granular ignition auxiliary propellant 13 is accommodated in the burnout container 11. In addition, the ignition assisting propellant 13 makes its web size W larger than the main propellant 12. The definition of the web size W is shown in FIG. Specifically, FIG. 4A shows a cylindrical non-porous web size W, FIG. 4B shows a cylindrical single-hole web size W, and FIG. 4C shows a hexagonal 19-hole web size. Each W is illustrated. As long as the web size W is larger than the main propellant 12, the shape of the auxiliary ignition propellant 13 can be a single cylinder hole, a seven cylinder hole, a nineteen cylinder hole, a nineteen hexagonal hole, etc. .

  By accommodating such an ignition auxiliary propellant 13 together with the main propellant 12 in the burn-out container 11, the flame of the ignition agent 15 ignited by a fire pipe (not shown) is injected into the main via the ignition auxiliary propellant 13. The propellant 12 is smoothly transmitted to the medicine 12 and the low temperature ignitability of the main propellant 12 is improved. At this time, the ignition auxiliary propellant 13 can be accommodated in a separated state packed in a medicine bag as in the first embodiment shown in FIG. 1, or the main firing as in the second embodiment shown in FIG. The medicine 12 can be mixed and dispersed in the burnout container 11. However, in any of the embodiments, it is preferable to arrange at least the innermost peripheral edge portion in the burnout container 11 (the portion in contact with the ignition cartridge 11c). This is because, if the ignition auxiliary propellant 13 is disposed at a site away from the igniter 15, the effect of improving the low temperature ignitability of the main propellant 12 is reduced.

  The ignition auxiliary propellant 13 can be used as long as it is 3 to 30% by mass with respect to 100% by mass of the total mass of the main propellant 12 and the ignition auxiliary propellant 13, but should be 5 to 25% by mass. Is preferable, and 5 to 20% by mass is more preferable. When the blending ratio of the ignition auxiliary propellant 13 is less than 3% by weight, the effect as the ignition auxiliary propellant 13 cannot be sufficiently exerted, and it becomes difficult to improve the ignitability of the main propellant 12. On the other hand, when the blending ratio of the ignition assisting propellant 13 exceeds 30% by weight, the combustion temperature tends to be too high and the erosion of the gun barrel tends to increase.

  Specific examples of the present invention will be described below, but the present invention is not limited thereto. First, a closed bomb combustion test used for measuring combustion characteristics in the following test will be described.

<Sealed bomb combustion test>
As shown in FIG. 3, a cylinder-shaped combustion space 51 having a volume of 150 ml is provided in the bomb body 50, and a combustion characteristic measurement target (a main propellant 12 or an ignition-assisted launch) is provided in the combustion space 51. The medicine 13) is loaded. A plug body 52 that seals the inside of the combustion space 51 is attached to one end side of the bomb body 50, and is detachable by a bolt 53. The volume of the combustion space 51 is calculated by subtracting the volume of a part of the plug body 52 from the volume of a cylindrical body having a diameter of 35 mm and a depth of 165 mm. An ignition device 56 is connected to one end side of the bomb main body 50 via a connection wiring 54, and the connection wiring 55 is connected to the bomb main body 50.

  A pair of electrodes 57, 58 are attached to the inner end surface of the plug body 52 in the combustion space 51, the connection wiring 54 is connected to one electrode 57, and the other electrode 58 is connected to the bomb body 50. Yes. An ignition ball (with black powder 0.5 g) 59 is attached to both electrodes 57 and 58 via connection lines. When the ignition device 56 is operated, the ignition ball 59 is ignited through the connection wires 54 and 55, the electrodes 57 and 58, and the main propellant 12 and the ignition auxiliary propellant 13 in the combustion space 51 are ignited and burned. It is supposed to let you.

  A gas vent valve 60 is attached to the side surface of the bomb body 50 and communicates with the combustion space 51 via a sampling pipe 61. The gas in the combustion space 51 is sampled from the degassing valve 60, and its combustion characteristics can be evaluated. A pressure transducer 62 is attached to the other end surface of the bomb body 50 and communicates with the combustion space 51 via a communication pipe 63. The pressure converter 62 can determine the ignition delay time and the gas generation rate.

  Then, the main propellant 12 and the ignition auxiliary propellant 13 are loaded into the combustion space 51 with the plug body 52 removed. The drug amount loaded at that time was set to a specific gravity of 0.1 g / ml. Next, the plug 52 is closed, and the ignition device 56 ignites the propellant 12 and the ignition auxiliary propellant 13 in the combustion space 51. Then, the relationship between the combustion time and the combustion pressure at the time of combustion is measured by an oscilloscope (not shown) via the pressure converter 62, and the ignition delay time and the gas generation speed can be obtained. The time from the start of energization to the ignition ball until the pressure reached 10% of the maximum pressure was defined as the ignition delay time. Further, ΔP / Δt at a combustion ratio of 0.2 to 0.8 was defined as a gas generation rate.

<Shooting test>
Next, a shooting test method will be described. As a shooting test device, a shooting test device having a chamber and a barrel (about 4 m in length) is equivalent to a 155 mm shell, and after loading a bullet with a mass of 44 kg in front of the chamber, After loading the medicine into the medicine chamber and closing the medicine chamber with the closing device, the projectile is ignited by the operation of the fire tube, and the bullet is made to fly. At that time, the pressure in the chamber is measured to obtain a pressure-time curve.

  The propellant used has an outer diameter D1 = 155 mm, a length L1 = 150 mm, and a cavity diameter D2 = 35 mm. The composition of the burnout container is 57% by mass of nitrocellulose, 28% by mass of kraft pulp, and binder resin 14 The mass was 1% by mass and the stabilizer was 1% by mass. In addition, 5 g of black powder and 5 g of porous single-base propellant (CBI) that have been used for this type of projectile are conventionally used in this type of projectile, and these are placed in a cloth bag and used as a spark cartridge. It shall be provided inside.

(Production example 1-1 of main propellant)
Diethylene glycol dinitrate (DEGN) 27.0% by mass, nitrocellulose (NC) 33.0% by mass, nitroguanidine (NQ) 39.0% by mass, stabilizer 1.0% by mass, web size 1.4 mm Molded into 19 hexagonal holes. As the production method, a known solvent drawing method comprising kneading, drawing, cutting, and drying steps was used.

(Production example 1-2 of main propellant)
Diethylene glycol dinitrate (DEGN) 40.0% by mass, nitrocellulose (NC) 12.0% by mass, nitroguanidine (NQ) 47.0% by mass, stabilizer 1.0% by mass, Production Example 1-1 By the same method, it was molded into hexagonal 19 holes with a web size of 1.6 mm.

The ignition delay time and gas generation rate of the obtained main propellant 1-1 and 1-2 at low temperatures were measured by the above-described closed bomb combustion test. Specifically, the ignition delay time and the gas generation rate were measured using the main propellants 1-1 and 1-2 adjusted to -40 ° C. The results are shown in Table 1.

(Ignition auxiliary propellant production example 2-1)
A double base propellant comprising 35.0% by weight of diethylene glycol dinitrate (DEGN), 64.0% by weight of nitrocellulose (NC), and 1.0% by weight of stabilizer, and the web size was obtained in the same manner as in Production Example 1-1. It was molded into a 2.0 mm single-hole tube.

(Ignition auxiliary propellant production example 2-2)
A single base propellant comprising 91.0% by mass of nitrocellulose (NC), 3.5% by mass of a stabilizer, and 5.5% by mass of a plasticizer was used. Molded into a tubular hole.

(Ignition auxiliary propellant production example 2-3)
A porous single base propellant (CBI) generally used in this type of propellant was formed into a single-hole tubular tube having a web size of 0.6 mm by the same method as in Production Example 1-1. .

(Ignition auxiliary propellant production example 2-4)
A powdery (average particle diameter of 0.8 mm) black powder that has been conventionally used in this type of propellant was used. In the said manufacture example 2-4, since the particle size of each black explosive has dispersion | variation, a web size is not decided uniquely.

For each of the obtained ignition auxiliary propellants, the temperature was adjusted to −40 ° C., and the ignition delay time and gas generation rate at low temperatures were measured in the same manner as the main propellants 1-1 and 1-2. The results are shown in Table 2.

Example 1
The main propellant production example 1-1 was weighed so that the main propellant was 90% by mass, and the ignition auxiliary propellant production example 2-1 was 10% by mass. The propellant was produced by storing the medicine and a spark-assisted propellant in a cloth bag. In addition, the ignition auxiliary propellant put in the cloth bag was installed on the innermost peripheral edge of the burnout container.

(Examples 2-9)
The propellant shown in Table 3 was weighed so as to have the mass ratio shown in Table 3, and the propellant was manufactured in the same manner as in Example 1. In addition, the blending ratio of the ignition auxiliary propellant shown in Table 3 is expressed as a mass ratio of the ignition auxiliary propellant with respect to 100% by mass of the total mass of the main propellant and the ignition auxiliary propellant.

(Examples 10 to 11)
The main propellant production example 1-1 and the ignition auxiliary propellant production example 2-1 were mixed and dispersed in the proportion of the ignition auxiliary propellant shown in Table 3 and housed in the burnout container to produce a propellant.

(Comparative Examples 1-4)
The composition was weighed so as to have the structure shown in Table 3, and a propellant was produced in the same manner as in Example 1.

  Each obtained charge was adjusted to −40 ° C. and then subjected to a shooting test using the above shooting test apparatus. Table 3 also shows the ignition delay time at low temperatures and the evaluation results of the corrosion resistance obtained in this way. In addition, evaluation of erosion property was performed as follows.

<Bake erosion>
The erodibility was evaluated by the combustion temperature, which is an index of erodibility. In order to reduce the erosion generated on the inner surface of the gun barrel, it is preferable to lower the combustion temperature as much as possible. The combustion temperature was calculated by a thermal equilibrium calculation known in the field and evaluated according to the following evaluation criteria.
◎: Combustion temperature calculated by thermal equilibrium calculation is less than 2800K ○: Combustion temperature calculated by thermal equilibrium calculation is from 2800K to less than 2850K △: Combustion temperature calculated by thermal equilibrium calculation is from 2850K to less than 2900K

  Based on the results in Table 3, the ignition delay time is shorter than the main propellant and the gas generation rate is moderately slower than the main propellant (the amount of gas generated per unit time is small). In Examples 1 to 11 where the tests were conducted, since the low temperature ignitability of the main propellant was improved, the ignition delay time was within 1.7 seconds, and the conventional propellant using nitroglycerin as the nitro plasticizer. The ignition delay time was equal to or shorter than (the ignition delay time is within 2 seconds at the latest).

  In particular, it was confirmed that Examples 1 to 5 were excellent in ignitability with an ignition delay time of 1.2 seconds or less and that erosion was also reliably suppressed. On the other hand, in Example 8 where the mass ratio of the ignition assisting propellant is relatively high at 30%, it can be used as a propellant, but it is clear that the combustion temperature tends to increase and the erosion of the gun barrel tends to increase. became. Further, in Example 9 where the mass ratio of the ignition auxiliary propellant was relatively small at 3%, the ignition delay time was 1.5 seconds, which was slightly inferior to Examples 1-8. Furthermore, with respect to Examples 10 and 11 in which the method of arranging the ignition auxiliary propellant was mixed and dispersed, the ignition delay time was generally delayed as compared with Examples 1 to 8 which were separately housed. As a result, it was confirmed that the separation accommodation is preferable to the mixed dispersion accommodation.

  On the other hand, in Comparative Example 1, since the gas generation rate of the ignition auxiliary propellant is faster than that of the main propellant, the ignition delay time at a low temperature in the shooting test is 2.5 seconds, which is difficult to use as a propellant. It became clear that there was. Further, from the result of Comparative Example 2, it was found that the low temperature ignitability of the main propellant cannot be improved even when black powder is used in combination. In the main propellants of Comparative Examples 3 to 4 in which no ignition auxiliary propellant was blended, the ignition delay time was 3 seconds or more, and it became clear that it was difficult to use as a propellant.

10 Propellant 11 Burnout container 12 Main propellant 13 Auxiliary propellant 15 Ignition W W Web size

Claims (6)

A propellant containing a main propellant consisting of a triple base propellant containing diethylene glycol dinitrate as a nitro plasticizer in a burnout container,
In the burnout container, an ignition auxiliary propellant containing nitrocellulose is accommodated together with the main propellant,
The firing charge is characterized in that the ignition auxiliary propellant has an ignition delay time shorter than that of the main propellant and a gas generation rate is slower than that of the main propellant.   The propellant according to claim 1, wherein the ignition auxiliary propellant has a composition with a higher relative proportion of nitrocellulose than the main propellant.   The propellant charge according to claim 1 or claim 2, wherein the ignition assisting propellant is a single base propellant or a double base propellant.   The propellant according to any one of claims 1 to 3, wherein the ignition assisting propellant has a larger web size than the main propellant.   The propellant according to any one of claims 1 to 4, wherein the ignition auxiliary propellant is 5 to 25 mass% with respect to a total mass of 100 mass% of the main propellant and the ignition auxiliary propellant. . The burnout container has an axial through hole in the radial center, and an ignition agent is arranged on the inner peripheral surface of the burnout container,
The firing charge according to any one of claims 1 to 5, wherein the ignition assisting propellant is disposed at least on an innermost peripheral edge portion in the burnout container.

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